GIII BL450 AIRFOIL (giiin-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL450 AIRFOIL (giiin-il) Reynolds number: 100,000 Max Cl/Cd: 40.65 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiin-il-100000-n5.txt Download as CSV file: xf-giiin-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL450 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5195 0.09852 0.09341 0.0077 1.0000 0.0493
-8.000 -0.5197 0.09437 0.08930 0.0026 1.0000 0.0498
-7.750 -0.5200 0.08978 0.08471 -0.0042 1.0000 0.0500
-7.500 -0.5176 0.08532 0.08013 -0.0104 1.0000 0.0503
-7.250 -0.5067 0.08129 0.07620 -0.0092 1.0000 0.0509
-7.000 -0.4961 0.07801 0.07296 -0.0087 1.0000 0.0520
-6.750 -0.4860 0.07446 0.06940 -0.0105 1.0000 0.0534
-6.500 -0.4749 0.07071 0.06559 -0.0130 1.0000 0.0550
-6.250 -0.4613 0.06700 0.06162 -0.0168 1.0000 0.0571
-6.000 -0.4466 0.06403 0.05822 -0.0192 1.0000 0.0577
-5.750 -0.4322 0.05973 0.05398 -0.0194 1.0000 0.0581
-5.500 -0.4173 0.05619 0.05050 -0.0194 1.0000 0.0590
-5.250 -0.4009 0.05319 0.04746 -0.0195 1.0000 0.0602
-5.000 -0.3832 0.05039 0.04456 -0.0197 1.0000 0.0618
-4.500 -0.3470 0.04517 0.03897 -0.0195 1.0000 0.0687
-4.250 -0.3300 0.04292 0.03667 -0.0189 1.0000 0.0716
-3.750 -0.2933 0.03740 0.03056 -0.0159 1.0000 0.0552
-3.500 -0.2587 0.03442 0.02690 -0.0167 0.9903 0.0501
-3.000 -0.1867 0.02977 0.02164 -0.0203 0.9653 0.0502
-2.750 -0.1511 0.02775 0.01936 -0.0219 0.9523 0.0505
-2.500 -0.1173 0.02621 0.01783 -0.0236 0.9390 0.0527
-2.250 -0.0828 0.02482 0.01621 -0.0246 0.9254 0.0543
-2.000 -0.0496 0.02346 0.01460 -0.0251 0.9113 0.0545
-1.750 -0.0188 0.02237 0.01329 -0.0250 0.8961 0.0557
-1.500 0.0101 0.02159 0.01220 -0.0244 0.8794 0.0579
-1.250 0.0370 0.02056 0.01117 -0.0238 0.8622 0.0590
-1.000 0.0636 0.01975 0.01031 -0.0231 0.8447 0.0600
-0.750 0.0898 0.01910 0.00962 -0.0222 0.8271 0.0621
-0.500 0.1159 0.01855 0.00898 -0.0212 0.8088 0.0648
-0.250 0.1420 0.01800 0.00835 -0.0202 0.7903 0.0662
0.000 0.1672 0.01732 0.00773 -0.0192 0.7701 0.0678
0.250 0.1916 0.01682 0.00727 -0.0180 0.7471 0.0711
0.500 0.2159 0.01641 0.00683 -0.0167 0.7222 0.0742
0.750 0.2401 0.01608 0.00639 -0.0153 0.6964 0.0763
1.000 0.2643 0.01575 0.00599 -0.0141 0.6724 0.0801
1.250 0.2894 0.01557 0.00570 -0.0132 0.6481 0.0849
1.500 0.3153 0.01548 0.00545 -0.0123 0.6266 0.0887
1.750 0.3413 0.01535 0.00524 -0.0116 0.6064 0.0960
2.000 0.3676 0.01531 0.00509 -0.0110 0.5860 0.1038
2.250 0.3940 0.01526 0.00499 -0.0104 0.5649 0.1189
2.500 0.4286 0.01302 0.00509 -0.0107 0.5410 0.9643
2.750 0.4655 0.01321 0.00505 -0.0123 0.5152 1.0000
3.000 0.4902 0.01341 0.00510 -0.0115 0.4904 1.0000
3.250 0.5146 0.01365 0.00517 -0.0106 0.4637 1.0000
3.500 0.5391 0.01390 0.00529 -0.0099 0.4326 1.0000
3.750 0.5634 0.01420 0.00541 -0.0091 0.3957 1.0000
4.000 0.5873 0.01456 0.00556 -0.0083 0.3496 1.0000
4.250 0.6106 0.01506 0.00576 -0.0076 0.3003 1.0000
4.500 0.6336 0.01566 0.00606 -0.0069 0.2639 1.0000
4.750 0.6571 0.01625 0.00647 -0.0063 0.2378 1.0000
5.000 0.6809 0.01683 0.00692 -0.0057 0.2171 1.0000
5.250 0.7047 0.01739 0.00739 -0.0051 0.1993 1.0000
5.500 0.7286 0.01795 0.00788 -0.0046 0.1838 1.0000
5.750 0.7525 0.01851 0.00839 -0.0040 0.1697 1.0000
6.000 0.7762 0.01911 0.00894 -0.0035 0.1575 1.0000
6.250 0.7994 0.01975 0.00949 -0.0029 0.1468 1.0000
6.500 0.8232 0.02034 0.01010 -0.0024 0.1364 1.0000
6.750 0.8463 0.02103 0.01077 -0.0018 0.1281 1.0000
7.000 0.8692 0.02172 0.01144 -0.0012 0.1205 1.0000
7.250 0.8922 0.02247 0.01220 -0.0006 0.1136 1.0000
7.500 0.9149 0.02322 0.01296 0.0000 0.1077 1.0000
7.750 0.9371 0.02408 0.01381 0.0006 0.1026 1.0000
8.000 0.9596 0.02488 0.01470 0.0012 0.0973 1.0000
8.250 0.9812 0.02577 0.01555 0.0018 0.0933 1.0000
8.500 1.0031 0.02675 0.01664 0.0024 0.0894 1.0000
8.750 1.0247 0.02769 0.01768 0.0030 0.0854 1.0000
9.000 1.0456 0.02866 0.01865 0.0036 0.0823 1.0000
9.250 1.0660 0.02985 0.01991 0.0043 0.0796 1.0000
9.500 1.0863 0.03103 0.02130 0.0050 0.0764 1.0000
9.750 1.1058 0.03215 0.02251 0.0056 0.0736 1.0000
10.000 1.1248 0.03329 0.02366 0.0063 0.0714 1.0000
10.250 1.1428 0.03479 0.02529 0.0070 0.0695 1.0000
10.500 1.1591 0.03642 0.02721 0.0078 0.0672 1.0000
10.750 1.1745 0.03795 0.02893 0.0086 0.0650 1.0000
11.000 1.1895 0.03934 0.03044 0.0094 0.0632 1.0000
11.250 1.2048 0.04078 0.03190 0.0102 0.0618 1.0000
11.500 1.2159 0.04283 0.03412 0.0111 0.0605 1.0000
11.750 1.2201 0.04533 0.03700 0.0123 0.0591 1.0000
12.000 1.2208 0.04784 0.03982 0.0135 0.0578 1.0000
12.250 1.2181 0.05036 0.04258 0.0147 0.0567 1.0000
12.500 1.2139 0.05306 0.04548 0.0154 0.0558 1.0000
12.750 1.2087 0.05600 0.04860 0.0155 0.0550 1.0000
13.000 1.2022 0.05930 0.05206 0.0149 0.0543 1.0000
13.250 1.1938 0.06311 0.05603 0.0138 0.0538 1.0000
13.500 1.1824 0.06761 0.06069 0.0119 0.0534 1.0000
13.750 1.1654 0.07327 0.06654 0.0089 0.0531 1.0000
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Polar data table (+)
Polar graphs
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